EP2663777A1 - Turbofan engine - Google Patents

Turbofan engine

Info

Publication number
EP2663777A1
EP2663777A1 EP12702301.8A EP12702301A EP2663777A1 EP 2663777 A1 EP2663777 A1 EP 2663777A1 EP 12702301 A EP12702301 A EP 12702301A EP 2663777 A1 EP2663777 A1 EP 2663777A1
Authority
EP
European Patent Office
Prior art keywords
casing
housing
suction
engine according
wall
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Granted
Application number
EP12702301.8A
Other languages
German (de)
French (fr)
Other versions
EP2663777B1 (en
Inventor
Cédric Morel
Alexandre Alfred Gaston Vuillemin
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Safran Aircraft Engines SAS
Original Assignee
SNECMA SAS
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by SNECMA SAS filed Critical SNECMA SAS
Publication of EP2663777A1 publication Critical patent/EP2663777A1/en
Application granted granted Critical
Publication of EP2663777B1 publication Critical patent/EP2663777B1/en
Active legal-status Critical Current
Anticipated expiration legal-status Critical

Links

Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/66—Combating cavitation, whirls, noise, vibration or the like; Balancing
    • F04D29/661—Combating cavitation, whirls, noise, vibration or the like; Balancing especially adapted for elastic fluid pumps
    • F04D29/663—Sound attenuation
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C6/00—Plural gas-turbine plants; Combinations of gas-turbine plants with other apparatus; Adaptations of gas-turbine plants for special use
    • F02C6/04—Gas-turbine plants providing heated or pressurised working fluid for other apparatus, e.g. without mechanical power output
    • F02C6/06—Gas-turbine plants providing heated or pressurised working fluid for other apparatus, e.g. without mechanical power output providing compressed gas
    • F02C6/08—Gas-turbine plants providing heated or pressurised working fluid for other apparatus, e.g. without mechanical power output providing compressed gas the gas being bled from the gas-turbine compressor
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
    • F02C7/04—Air intakes for gas-turbine plants or jet-propulsion plants
    • F02C7/045—Air intakes for gas-turbine plants or jet-propulsion plants having provisions for noise suppression
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02K—JET-PROPULSION PLANTS
    • F02K3/00—Plants including a gas turbine driving a compressor or a ducted fan
    • F02K3/02—Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber
    • F02K3/04—Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber the plant including ducted fans, i.e. fans with high volume, low pressure outputs, for augmenting the jet thrust, e.g. of double-flow type
    • F02K3/06—Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber the plant including ducted fans, i.e. fans with high volume, low pressure outputs, for augmenting the jet thrust, e.g. of double-flow type with front fan
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/40—Casings; Connections of working fluid
    • F04D29/52—Casings; Connections of working fluid for axial pumps
    • F04D29/522—Casings; Connections of working fluid for axial pumps especially adapted for elastic fluid pumps
    • F04D29/526—Details of the casing section radially opposing blade tips
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/66—Combating cavitation, whirls, noise, vibration or the like; Balancing
    • F04D29/68—Combating cavitation, whirls, noise, vibration or the like; Balancing by influencing boundary layers
    • F04D29/681—Combating cavitation, whirls, noise, vibration or the like; Balancing by influencing boundary layers especially adapted for elastic fluid pumps
    • F04D29/682—Combating cavitation, whirls, noise, vibration or the like; Balancing by influencing boundary layers especially adapted for elastic fluid pumps by fluid extraction
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T50/00—Aeronautics or air transport
    • Y02T50/60—Efficient propulsion technologies, e.g. for aircraft

Definitions

  • the present invention relates to a turbofan engine for an aircraft, particularly for an aircraft.
  • Cell noise is due to the interaction of airflow and aircraft surface obstacles or irregularities, such as landing gear, leading edge slats, flight, etc.
  • the engine noise mainly comprises a jet noise, due to the rapid ejection of hot gases through the nozzle, and a fan noise, due to interactions between the flow of the jet engine. air and the fixed structure, which are generated by the blades of the fan supplying the secondary flow.
  • a turbofan engine comprises a blower wheel carrying vanes and rotating in an annular housing. Downstream of the blower, part of the flow is directed towards a primary stream in which circulates a primary stream compressed by a low pressure compressor and a high pressure compressor for the supply of a combustion chamber, another part of the flow from the fan being directed towards a secondary vein in which extends a rectifying vane.
  • the acoustic spectrum of a blower can be decomposed into a tonal part and a broadband part whose importance increases with the appearance of turbojets with very high dilution rates, for which the secondary flow is important.
  • the sources of broadband noise in a blower are multiple, a dominant source being the interaction between the wake of the blower wheel and the stator, in particular the rectifier blade.
  • US Pat. No. 3,730,639 proposes to equip the outer casing of the blower with the aid of suction means comprising an air inlet opening, formed by a slot, disposed upstream of the radially outer ends of the blades of the blower wheel, and a suction pump.
  • a known solution is to provide air injection means at the vortex zones of the blower.
  • air channels must be made in the blades of the wheel of blower, which increases the complexity of realization of these blades, especially when they are made of composite material.
  • the invention aims in particular to provide a simple, effective and economical solution to this problem.
  • turbofan engine comprising a fan wheel bearing vanes and surrounded by an annular casing, characterized in that the casing comprises air suction means in the annular clearance formed between the casing and the radially outer ends of the blades of the blower wheel.
  • the suction means thus positioned make it possible to suck up the turbulent flow at the top of the blades of the fan wheel so that it does not interact with the downstream rectifying blade, and thus substantially reduce the noise generated by the fan. interaction between the wake of the fan wheel and the stator, in particular with the downstream corrugating vane.
  • the suction means comprise a mouth formed by at least one inlet slot made in the inner wall of the housing and connected to a suction channel extending downstream.
  • this inlet slit of the suction means is located axially facing only the upstream portion of the rope of the blades of the fan wheel at their radially outer end.
  • the suction slot only facing the upstream part of the rope allows to suck the game flow from the birth of the leading edge corner vortex. Simulations have shown that there are several birthplaces of vortex vortices, the most energetic being located approximately on the first third of the rope at the top of the blade.
  • the slots have been positioned in the area where the most vortex activity is created.
  • the inlet slit of the suction means is situated axially facing only the upstream third of the rope of the vanes of the fan wheel at their radially outer end.
  • the inlet slot has an axial dimension of between 3 and 10% of the blade string at their radially outer end.
  • the inlet slit is annular or formed of a plurality of orifices distributed around the axis of the fan.
  • the suction means may comprise a suction pump housed in the housing.
  • the suction means comprise at least two inlet slots formed in the inner wall of the housing and axially offset relative to each other.
  • the air suction means comprise an annular collector housed in the housing and connected to the inlet slit (s) by suction channels.
  • the air suction means further comprise air outlet orifices formed downstream of the blower wheel in the outer wall or in the inner wall of the fan casing.
  • outlets of the air suction means may be formed in the inner wall of the fan casing downstream of the blower outlet rectifying blade.
  • FIG. 1 is a schematic sectional view of a portion of a turbojet according to a first embodiment of the invention
  • FIG. 2 is a view corresponding to FIG. 2, of a second embodiment of the invention. invention
  • FIG. 3 is a schematic view, enlarged and in section, of a portion of a turbojet according to a third embodiment of the invention.
  • FIG. 1 represents a part of a turbojet comprising a fan wheel 1 carrying blades 2 and surrounded by an annular casing 3. Downstream of the fan, part of the fluid flow is directed towards a primary stream 4 in which a primary flow intended to be compressed by a low pressure compressor and a high pressure compressor to feed the combustion chamber (not shown), another part of the flow from the fan being directed towards a secondary vein 5 in which extends a vane straightener 6, also called OGV (Outlet Guide Vane).
  • OGV Outlet Guide Vane
  • radial structural arms 7 Downstream of the blade 6 are radial structural arms 7 having a high mechanical strength and also extending into the secondary vein 5.
  • the casing 3 comprises air suction means opening into the annular clearance 8 formed between the casing 3 and the radially outer ends of the vanes 2 of the blower wheel 1.
  • the air suction means comprise at least one suction channel 9 comprising a mouth opening in the annular clearance 8 above, formed by an inlet slot 10 formed in the internal wall 1 1 of the housing 3.
  • the slot 10 extends over the entire circumference of the inner wall of the housing 3 and each suction channel 9 extending downstream opens on the outer wall 12 of the housing in a zone determined, for example a zone located axially downstream of the rectifying blade 6 to blow the air outwards in order to glue the boundary layer on the outer wall 12 of the housing when necessary.
  • the dimensions and the position of the slits 10 and the suction channels 9 are determined so that only a small part of the flow of air flowing through the fan is taken by the slot 10, for example between 0.5 and 2% of the total flow, preferably of the order of 1%.
  • the suction air flow rate is substantially proportional to the rotational speeds of the shaft of the low pressure turbine which drives the wheel 1 of the fan and which vary widely between the landing and takeoff phases.
  • the suction air flow rate depends on the radial clearance 8 between the outer ends of the blades 2 and the inner wall January 1 of the housing 3.
  • the inlet slit 10 has an axial dimension of between 3 and 10% of the chord of the blades 2 at their radially outer end.
  • the rope of a blade is the distance between its leading edge 13, that is to say its upstream edge, and its trailing edge 14, that is to say its downstream edge.
  • the inlet slit 10 of the suction means is located axially facing the only upstream half of the rope of the blades 2 at their radially outer end.
  • the inlet slit 10 therefore does not extend upstream of the ends of the blades or opposite the downstream half of the rope of the blades 2.
  • annular inlet slot 10 instead of an annular inlet slot 10, a series of orifices distributed circumferentially around the axis of the fan may be provided.
  • the pressure p 2 at the outlet of the or each suction channel 9 is smaller than the pressure pi at the inlet into the slot 10, the pressure difference making it possible to overcome the pressure losses in channel 9 and suck the air. It is therefore not necessary to equip the channel or channels 9 with a suction pump.
  • the suction channel 9 opens on the inner wall 1 1 of the casing 3, downstream of the rectifying blade 6, in an area where the pressure p 3 is greater than in the inlet slot 10. It is therefore necessary to equip the suction channel with a suction pump 15, housed in the housing 3.
  • the number and position of the channels 9 may vary depending on the applications.
  • the outer casing 3 comprises at least two inlet slots 10 formed in the inner wall January 1 of the housing 3 and axially offset relative to each other. Suction channels 9 extend downstream from each of the inlet slots 10 to an annular manifold 16 housed in the housing 3. The air in the manifold 16 is then sucked by means of a pump 15 and is ejected, either on the inner wall January 1 of the housing 3, or on the outer wall 12, in a similar manner to that described above.
  • the invention thus makes it possible, irrespective of the embodiment used, to take the air flow at the top of the fan blade 2 in order to limit the interaction between this highly turbulent flow and the rectifying blade. downstream. This significantly reduces the broadband noise generated by this interaction. The fraction taken from the flow rate of the fan being low, the efficiency of the fan is not substantially penalized.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)

Abstract

A bypass turbojet including a fan wheel carrying blades and surrounded by an annular casing, the casing including an air suction mechanism sucking air from an annular clearance formed between the casing and radially outer ends of the blades of the fan wheel. The air suction mechanism includes an inlet including at least one inlet slot formed in an inside wall of the casing and connected to a suction channel extending downstream. The inlet slot of the suction mechanism is situated axially in register solely with upstream portions of chords of the blades of the fan wheel at their radially outer ends.

Description

Turboréacteur à double flux  Double flow turbofan
La présente invention concerne un turboréacteur à double flux pour un aéronef, notamment pour un avion. The present invention relates to a turbofan engine for an aircraft, particularly for an aircraft.
La réduction des émissions sonores des avions dans les zones aéroportuaires est un enjeu majeur et des normes de plus en plus strictes sont imposées à cet effet.  The reduction of noise emissions from aircraft in airport areas is a major issue and increasingly stringent standards are imposed for this purpose.
Des efforts d'investigation ont permis d'identifier et de quantifier les principaux phénomènes responsables des niveaux de bruits importants générés par les avions en phase d'atterrissage et de décollage. On peut grossièrement séparer ces bruits en deux grandes catégories, à savoir le bruit de cellule et le bruit de moteurs.  Investigative efforts made it possible to identify and quantify the main phenomena responsible for the high levels of noise generated by planes landing and taking off. These noises can be roughly divided into two broad categories, namely cell noise and motor noise.
Le bruit de cellule est dû aux interactions de l'écoulement de l'air et des obstacles ou des irrégularités de surface de l'avion, tels que les trains d'atterrissage, les becs de bord d'attaque, les volets de bords de fuite, etc.  Cell noise is due to the interaction of airflow and aircraft surface obstacles or irregularities, such as landing gear, leading edge slats, flight, etc.
Dans le cas d'un turboréacteur à double flux, le bruit de moteur comprend principalement un bruit de jet, dû à l'éjection rapide de gaz chauds par la tuyère, et un bruit de soufflante, dû à des interactions entre l'écoulement d'air et la structure fixe, qui sont générées par les pales de la soufflante alimentant le flux secondaire.  In the case of a turbofan engine, the engine noise mainly comprises a jet noise, due to the rapid ejection of hot gases through the nozzle, and a fan noise, due to interactions between the flow of the jet engine. air and the fixed structure, which are generated by the blades of the fan supplying the secondary flow.
On rappelle qu'un turboréacteur à double flux comporte une roue de soufflante portant des aubes et tournant dans un carter annulaire. En aval de la soufflante, une partie du flux est dirigée vers une veine primaire dans laquelle circule un flux primaire compressé par un compresseur basse pression et par un compresseur haute pression pour l'alimentation d'une chambre de combustion, une autre partie du flux issu de la soufflante étant dirigée vers une veine secondaire dans laquelle s'étend un aubage redresseur.  It is recalled that a turbofan engine comprises a blower wheel carrying vanes and rotating in an annular housing. Downstream of the blower, part of the flow is directed towards a primary stream in which circulates a primary stream compressed by a low pressure compressor and a high pressure compressor for the supply of a combustion chamber, another part of the flow from the fan being directed towards a secondary vein in which extends a rectifying vane.
Le spectre acoustique d'une soufflante peut être décomposé en une partie tonale et une partie à large bande dont l'importance augmente avec l'apparition des turboréacteurs à très fort taux de dilution, pour lesquels le flux secondaire est important. The acoustic spectrum of a blower can be decomposed into a tonal part and a broadband part whose importance increases with the appearance of turbojets with very high dilution rates, for which the secondary flow is important.
Les sources du bruit à large bande dans une soufflante sont multiples, une source dominante étant l'interaction entre le sillage de la roue de soufflante et le stator, en particulier l'aubage redresseur.  The sources of broadband noise in a blower are multiple, a dominant source being the interaction between the wake of the blower wheel and the stator, in particular the rectifier blade.
Afin de minimiser les bruits générés par la soufflante, une solution consiste à optimiser le dessin des aubes du redresseur. Cependant, les contraintes de rendement du moteur en vitesse de croisière ne permettent pas d'adapter au mieux les aubes lors du fonctionnement à l'approche et au décollage.  In order to minimize the noise generated by the fan, one solution is to optimize the design of the stator vanes. However, the constraints of engine performance at cruising speed do not allow to better adapt the blades during operation on approach and takeoff.
Le brevet US 3 730 639 propose d'équiper le carter externe de la soufflante à l'aide de moyens d'aspiration comportant une ouverture d'entrée d'air, formée par une fente, disposée en amont des extrémités radialement externes des aubes de la roue de soufflante, et une pompe d'aspiration.  US Pat. No. 3,730,639 proposes to equip the outer casing of the blower with the aid of suction means comprising an air inlet opening, formed by a slot, disposed upstream of the radially outer ends of the blades of the blower wheel, and a suction pump.
De cette manière, une partie de la couche limite formée sur la paroi interne du carter externe est aspirée, de façon à limiter les interactions entre cette couche limite et les aubes de la roue de soufflante et réduire ainsi le bruit. Cette solution ne réduit pas sensiblement la composante dominante du bruit, générée par l'interaction entre le sillage de la roue de soufflante et l'aubage redresseur situé en aval.  In this way, a portion of the boundary layer formed on the inner wall of the outer casing is sucked, so as to limit the interactions between this boundary layer and the blades of the blower wheel and thus reduce the noise. This solution does not substantially reduce the dominant component of the noise, generated by the interaction between the wake of the blower wheel and the downstream rectifying blade.
De plus, la présence d'un jeu entre le carter et les extrémités des aubes de la roue de soufflante conduit à la génération de tourbillons par effet d'entraînement de l'écoulement de tête, qui sont porteurs d'un haut niveau d'énergie cinétique turbulente et qui, une fois mélangés avec la couche limite sur le carter, contribuent de façon significative au bruit à large bande d'interaction entre le sillage turbulent et l'aubage redresseur.  In addition, the presence of a clearance between the casing and the ends of the vanes of the blower wheel leads to the generation of swirls by entrainment effect of the head flow, which carry a high level of turbulent kinetic energy and, once mixed with the boundary layer on the crankcase, contribute significantly to the broadband noise of interaction between the turbulent wake and the rectifying blade.
Une solution connue consiste à prévoir des moyens d'injection d'air au niveau des zones tourbillonnaires de la soufflante. Pour cela, des canaux de passage d'air doivent être réalisés dans les aubes de la roue de soufflante, ce qui augmente la complexité de réalisation de ces aubes, en particulier lorsque celles-ci sont réalisées en matériau composite. A known solution is to provide air injection means at the vortex zones of the blower. For this, air channels must be made in the blades of the wheel of blower, which increases the complexity of realization of these blades, especially when they are made of composite material.
L'invention a notamment pour but d'apporter une solution simple, efficace et économique à ce problème.  The invention aims in particular to provide a simple, effective and economical solution to this problem.
A cet effet, elle propose un turboréacteur à double flux, comportant une roue de soufflante portant des aubes et entourée par un carter annulaire, caractérisé en ce que le carter comprend des moyens d'aspiration d'air dans le jeu annulaire formé entre le carter et les extrémités radialement externes des aubes de la roue de soufflante.  For this purpose, it proposes a turbofan engine, comprising a fan wheel bearing vanes and surrounded by an annular casing, characterized in that the casing comprises air suction means in the annular clearance formed between the casing and the radially outer ends of the blades of the blower wheel.
Les moyens d'aspiration ainsi positionnés permettent d'aspirer l'écoulement turbulent en sommet des aubes de la roue de soufflante pour qu'il n'interagisse pas avec l'aubage redresseur en aval, et ainsi de réduire sensiblement le bruit généré par l'interaction entre le sillage de la roue de soufflante et le stator, en particulier avec l'aubage redresseur situé en aval.  The suction means thus positioned make it possible to suck up the turbulent flow at the top of the blades of the fan wheel so that it does not interact with the downstream rectifying blade, and thus substantially reduce the noise generated by the fan. interaction between the wake of the fan wheel and the stator, in particular with the downstream corrugating vane.
Selon une caractéristique de l'invention, les moyens d'aspiration comprennent une embouchure formée par au moins une fente d'entrée réalisée dans la paroi interne du carter et reliée à un canal d'aspiration s'étendant vers l'aval.  According to one characteristic of the invention, the suction means comprise a mouth formed by at least one inlet slot made in the inner wall of the housing and connected to a suction channel extending downstream.
Avantageusement, cette fente d'entrée des moyens d'aspiration est située axialement en regard uniquement de la partie amont de la corde des aubes de la roue de soufflante à leur extrémité radialement externe.  Advantageously, this inlet slit of the suction means is located axially facing only the upstream portion of the rope of the blades of the fan wheel at their radially outer end.
Le positionnement de la fente d'aspiration uniquement en regard de la partie amont de la corde permet d'aspirer l'écoulement de jeu dès la naissance du tourbillon de coin de bord d'attaque. Des simulations ont en effet montré qu'il y avait plusieurs lieux de naissance de tourbillons de sommet d'aube, les plus énergétiques étant localisés approximativement sur le premier tiers de la corde en sommet de pale. Les fentes ont ainsi été positionnées dans la zone où le plus d'activité tourbillonnaire est créée. Ainsi, préférentiellement, la fente d'entrée des moyens d'aspiration est située axialement en regard uniquement du tiers amont de la corde des aubes de la roue de soufflante à leur extrémité radialement externe. The positioning of the suction slot only facing the upstream part of the rope allows to suck the game flow from the birth of the leading edge corner vortex. Simulations have shown that there are several birthplaces of vortex vortices, the most energetic being located approximately on the first third of the rope at the top of the blade. The slots have been positioned in the area where the most vortex activity is created. Thus, preferably, the inlet slit of the suction means is situated axially facing only the upstream third of the rope of the vanes of the fan wheel at their radially outer end.
De manière préférée, la fente d'entrée a une dimension axiale comprise entre 3 et 10 % de la corde des aubes à leur extrémité radialement externe.  Preferably, the inlet slot has an axial dimension of between 3 and 10% of the blade string at their radially outer end.
Ainsi, seule une faible fraction de débit est prélevée, de façon à ne pas pénaliser le rendement du moteur.  Thus, only a small fraction of flow is taken, so as not to penalize the efficiency of the engine.
Selon une autre caractéristique de l'invention, la fente d'entrée est annulaire ou formée d'une pluralité d'orifices répartis autour de l'axe de la soufflante.  According to another characteristic of the invention, the inlet slit is annular or formed of a plurality of orifices distributed around the axis of the fan.
Les moyens d'aspiration peuvent comprendre une pompe d'aspiration logée dans le carter.  The suction means may comprise a suction pump housed in the housing.
Selon une forme de réalisation de l'invention, les moyens d'aspiration comprennent au moins deux fentes d'entrée formées dans la paroi interne du carter et décalées axialement l'une par rapport à l'autre.  According to one embodiment of the invention, the suction means comprise at least two inlet slots formed in the inner wall of the housing and axially offset relative to each other.
De manière avantageuse, les moyens d'aspiration d'air comprennent un collecteur annulaire logé dans le carter et relié à la ou aux fentes d'entrées par des canaux d'aspiration.  Advantageously, the air suction means comprise an annular collector housed in the housing and connected to the inlet slit (s) by suction channels.
Les moyens d'aspiration d'air comprennent par ailleurs des orifices de sortie d'air, formés en aval de la roue de soufflante dans la paroi externe ou dans la paroi interne du carter de soufflante.  The air suction means further comprise air outlet orifices formed downstream of the blower wheel in the outer wall or in the inner wall of the fan casing.
Plus particulièrement, les orifices de sortie des moyens d'aspiration d'air peuvent être formés dans la paroi interne du carter de soufflante en aval de l'aubage redresseur de sortie de la soufflante.  More particularly, the outlets of the air suction means may be formed in the inner wall of the fan casing downstream of the blower outlet rectifying blade.
L'invention sera mieux comprise et d'autres détails, caractéristiques et avantages de l'invention apparaîtront à la lecture de la description suivante faite à titre d'exemple non limitatif en référence aux dessins annexés dans lesquels : la figure 1 est une vue schématique en coupe d'une partie d'un turboréacteur selon une première forme de réalisation de l'invention, la figure 2 est une vue correspondant à la figure 2, d'une deuxième forme de réalisation de l'invention, The invention will be better understood and other details, characteristics and advantages of the invention will appear on reading the following description given by way of non-limiting example with reference to the accompanying drawings in which: FIG. 1 is a schematic sectional view of a portion of a turbojet according to a first embodiment of the invention, FIG. 2 is a view corresponding to FIG. 2, of a second embodiment of the invention. invention,
- la figure 3 est une vue schématique, agrandie et en coupe, d'une partie d'un turboréacteur selon une troisième forme de réalisation de l'invention.  - Figure 3 is a schematic view, enlarged and in section, of a portion of a turbojet according to a third embodiment of the invention.
La figure 1 représente une partie d'un turboréacteur comportant une roue de soufflante 1 portant des aubes 2 et entourée par un carter annulaire 3. En aval de la soufflante, une partie du flux produit est dirigée vers une veine primaire 4 dans laquelle circule un flux primaire destiné à être compressé par un compresseur basse pression et par un compresseur haute pression pour alimenter la chambre de combustion (non représentée), une autre partie du flux issu de la soufflante étant dirigée vers une veine secondaire 5 dans laquelle s'étend un aubage redresseur 6, également appelé OGV (Outlet Guide Vane). Cet aubage redresseur 6 a pour effet de redresser le flux d'air secondaire s'échappant de la soufflante afin d'en limiter la giration.  FIG. 1 represents a part of a turbojet comprising a fan wheel 1 carrying blades 2 and surrounded by an annular casing 3. Downstream of the fan, part of the fluid flow is directed towards a primary stream 4 in which a primary flow intended to be compressed by a low pressure compressor and a high pressure compressor to feed the combustion chamber (not shown), another part of the flow from the fan being directed towards a secondary vein 5 in which extends a vane straightener 6, also called OGV (Outlet Guide Vane). This rectifying blade 6 has the effect of straightening the secondary air flow escaping from the fan to limit the gyration.
En aval de l'aubage 6 se trouvent des bras structuraux 7 radiaux présentant une résistance mécanique élevée et s'étendant également dans la veine secondaire 5.  Downstream of the blade 6 are radial structural arms 7 having a high mechanical strength and also extending into the secondary vein 5.
Selon l'invention, le carter 3 comprend des moyens d'aspiration d'air débouchant dans le jeu annulaire 8 formé entre le carter 3 et les extrémités radialement externes des aubes 2 de la roue de soufflante 1 .  According to the invention, the casing 3 comprises air suction means opening into the annular clearance 8 formed between the casing 3 and the radially outer ends of the vanes 2 of the blower wheel 1.
Dans la forme de réalisation représentée à la figure 1 , les moyens d'aspiration d'air comportent au moins un canal d'aspiration 9 comprenant une embouchure ouvrant dans le jeu annulaire 8 précité, formée par une fente d'entrée 10 réalisée dans la paroi interne 1 1 du carter 3. La fente 10 s'étend sur toute la circonférence de la paroi interne du carter 3 et chaque canal d'aspiration 9 s'étendant vers l'aval débouche sur la paroi externe 12 du carter dans une zone déterminée, par exemple une zone située axialement en aval de l'aubage redresseur 6 pour souffler de l'air vers l'extérieur afin de recoller la couche limite sur la paroi externe 12 du carter lorsque cela est nécessaire. In the embodiment shown in Figure 1, the air suction means comprise at least one suction channel 9 comprising a mouth opening in the annular clearance 8 above, formed by an inlet slot 10 formed in the internal wall 1 1 of the housing 3. The slot 10 extends over the entire circumference of the inner wall of the housing 3 and each suction channel 9 extending downstream opens on the outer wall 12 of the housing in a zone determined, for example a zone located axially downstream of the rectifying blade 6 to blow the air outwards in order to glue the boundary layer on the outer wall 12 of the housing when necessary.
Les dimensions et la position des fentes 10 et des canaux d'aspiration 9 sont déterminées de façon ce que seule une faible partie du débit d'air circulant au travers de la soufflante soit prélevée par la fente 10, par exemple entre 0,5 et 2 % du débit total, préférentiellement de l'ordre de 1 %.  The dimensions and the position of the slits 10 and the suction channels 9 are determined so that only a small part of the flow of air flowing through the fan is taken by the slot 10, for example between 0.5 and 2% of the total flow, preferably of the order of 1%.
Le débit d'air aspiré est sensiblement proportionnel aux vitesses de rotation de l'arbre de la turbine basse pression qui entraîne la roue 1 de la soufflante et qui varient largement entre les phases d'atterrissage et de décollage. Le débit d'air aspiré dépend du jeu radial 8 entre les extrémités externes des aubes 2 et la paroi interne 1 1 du carter 3.  The suction air flow rate is substantially proportional to the rotational speeds of the shaft of the low pressure turbine which drives the wheel 1 of the fan and which vary widely between the landing and takeoff phases. The suction air flow rate depends on the radial clearance 8 between the outer ends of the blades 2 and the inner wall January 1 of the housing 3.
La fente d'entrée 10 a une dimension axiale comprise entre 3 et 10 % de la corde des aubes 2 à leur extrémité radialement externe. On rappelle que la corde d'une aube est la distance entre son bord d'attaque 13, c'est-à-dire son bord amont, et son bord de fuite 14, c'est-à-dire son bord aval.  The inlet slit 10 has an axial dimension of between 3 and 10% of the chord of the blades 2 at their radially outer end. Remember that the rope of a blade is the distance between its leading edge 13, that is to say its upstream edge, and its trailing edge 14, that is to say its downstream edge.
La fente d'entrée 10 des moyens d'aspiration est située axialement en regard de la seule moitié amont de la corde des aubes 2 à leur extrémité radialement externe. La fente d'entrée 10 ne s'étend donc pas en amont des extrémités des aubes ou en regard de la moitié aval de la corde des aubes 2.  The inlet slit 10 of the suction means is located axially facing the only upstream half of the rope of the blades 2 at their radially outer end. The inlet slit 10 therefore does not extend upstream of the ends of the blades or opposite the downstream half of the rope of the blades 2.
A la place d'une fente d'entrée annulaire 10, on peut prévoir une série d'orifices répartis circonférentiellement autour de l'axe de la soufflante.  Instead of an annular inlet slot 10, a series of orifices distributed circumferentially around the axis of the fan may be provided.
Dans le cas de la figure 1 , la pression p2 en sortie du ou de chaque canal d'aspiration 9 est inférieure à la pression pi à l'entrée dans la fente 10, la différence de pression permettant de vaincre les pertes de charges dans le canal 9 et d'aspirer l'air. Il n'est donc pas utile d'équiper le ou les canaux 9 avec une pompe d'aspiration. Dans la forme de réalisation de la figure 2 au contraire, le canal d'aspiration 9 débouche sur la paroi interne 1 1 du carter 3, en aval de l'aubage redresseur 6, dans une zone où la pression p3 est plus forte que dans la fente d'entrée 10. Il est donc nécessaire d'équiper le canal d'aspiration avec une pompe d'aspiration 15, logée dans le carter 3. In the case of FIG. 1, the pressure p 2 at the outlet of the or each suction channel 9 is smaller than the pressure pi at the inlet into the slot 10, the pressure difference making it possible to overcome the pressure losses in channel 9 and suck the air. It is therefore not necessary to equip the channel or channels 9 with a suction pump. In the embodiment of FIG. 2, on the contrary, the suction channel 9 opens on the inner wall 1 1 of the casing 3, downstream of the rectifying blade 6, in an area where the pressure p 3 is greater than in the inlet slot 10. It is therefore necessary to equip the suction channel with a suction pump 15, housed in the housing 3.
Bien entendu, le nombre et la position des canaux 9 peuvent varier en fonction des applications.  Of course, the number and position of the channels 9 may vary depending on the applications.
Dans la forme de réalisation de la figure 3, le carter externe 3 comporte au moins deux fentes d'entrée 10 formées dans la paroi interne 1 1 du carter 3 et décalées axialement l'une par rapport à l'autre. Des canaux d'aspiration 9 s'étendent vers l'aval depuis chacune des fentes d'entrée 10 jusqu'à un collecteur annulaire 16 logé dans le carter 3. L'air dans le collecteur 16 est ensuite aspiré à l'aide d'une pompe 15 puis est éjecté, soit sur la paroi interne 1 1 du carter 3, soit sur la paroi externe 12, d'une manière similaire à celle décrite précédemment.  In the embodiment of Figure 3, the outer casing 3 comprises at least two inlet slots 10 formed in the inner wall January 1 of the housing 3 and axially offset relative to each other. Suction channels 9 extend downstream from each of the inlet slots 10 to an annular manifold 16 housed in the housing 3. The air in the manifold 16 is then sucked by means of a pump 15 and is ejected, either on the inner wall January 1 of the housing 3, or on the outer wall 12, in a similar manner to that described above.
L'invention permet ainsi, quelle que soit la forme d'exécution utilisée, de prélever l'écoulement d'air en sommet d'aube 2 de soufflante afin de limiter l'interaction entre cet écoulement à forte turbulence et l'aubage redresseur 6 situé en aval. Cela permet de réduire sensiblement le bruit à large bande généré par cette interaction. La fraction prélevée du débit de la soufflante étant faible, le rendement de la soufflante n'est pas sensiblement pénalisé.  The invention thus makes it possible, irrespective of the embodiment used, to take the air flow at the top of the fan blade 2 in order to limit the interaction between this highly turbulent flow and the rectifying blade. downstream. This significantly reduces the broadband noise generated by this interaction. The fraction taken from the flow rate of the fan being low, the efficiency of the fan is not substantially penalized.

Claims

REVENDICATIONS
1 . Turboréacteur à double flux, comportant une roue de soufflante (1 ) portant des aubes (2) et entourée par un carter annulaire (3), le carter (3) comprenant des moyens d'aspiration d'air (9, 10) dans le jeu annulaire (8) formé entre le carter (3) et les extrémités radialement externes des aubes (2) de la roue de soufflante (1 ), les moyens d'aspiration comprenant une embouchure formée par au moins une fente d'entrée (10) réalisée dans la paroi interne (1 1 ) du carter (3) et reliée à un canal d'aspiration (9) s'étendant vers l'aval, caractérisé en ce que la fente d'entrée (10) des moyens d'aspiration est située axialement, en regard uniquement de la partie amont de la corde des aubes (2) de la roue de soufflante à leur extrémité radialement externe. 1. A turbofan engine comprising a blower wheel (1) carrying vanes (2) and surrounded by an annular housing (3), the casing (3) comprising air intake means (9, 10) in the annular clearance (8) formed between the casing (3) and the radially outer ends of the blades (2) of the blower wheel (1), the suction means comprising a mouth formed by at least one inlet slit (10). ) made in the inner wall (1 1) of the housing (3) and connected to a suction channel (9) extending downstream, characterized in that the inlet slot (10) means suction is located axially, facing only the upstream portion of the blade rope (2) of the blower wheel at their radially outer end.
2. Turboréacteur selon la revendication 1 , caractérisé en ce que la fente d'entrée (10) a une dimension axiale comprise entre 3 et 10 % de la corde des aubes (2) à leur extrémité radialement externe.  2. Turbojet engine according to claim 1, characterized in that the inlet slot (10) has an axial dimension of between 3 and 10% of the blade string (2) at their radially outer end.
3. Turboréacteur selon la revendication 1 ou 2, caractérisé en ce que la fente d'entrée (10) est annulaire ou formée d'une pluralité d'orifices répartis autour de l'axe de la soufflante.  3. Turbojet engine according to claim 1 or 2, characterized in that the inlet slit (10) is annular or formed of a plurality of orifices distributed around the axis of the fan.
4. Turboréacteur selon l'une des revendications 1 à 3, caractérisé en ce que les moyens d'aspiration comprennent une pompe d'aspiration (15) logée dans le carter (3).  4. Turbojet engine according to one of claims 1 to 3, characterized in that the suction means comprises a suction pump (15) housed in the housing (3).
5. Turboréacteur selon l'une des revendications 1 à 4, caractérisé en ce que les moyens d'aspiration comprennent au moins deux fentes d'entrée (10) formées dans la paroi interne (1 1 ) du carter (3) et décalées axialement l'une par rapport à l'autre.  5. Turbojet engine according to one of claims 1 to 4, characterized in that the suction means comprise at least two inlet slots (10) formed in the inner wall (1 1) of the housing (3) and axially offset one with respect to the other.
6. Turboréacteur selon l'une des revendications 1 à 4, caractérisé en ce que les moyens d'aspiration d'air comprennent un collecteur annulaire (16) logé dans le carter (3) et relié à la ou aux fentes d'entrée (10) par des canaux d'aspiration (9). 6. Turbojet engine according to one of claims 1 to 4, characterized in that the air suction means comprise an annular collector (16) housed in the housing (3) and connected to the inlet slit or slots ( 10) by suction channels (9).
7. Turboréacteur selon l'une des revendications 1 à 6, caractérisé en ce que les moyens d'aspiration d'air comprennent des orifices de sortie d'air (15), formés en aval de la roue de soufflante (1 ) dans la paroi externe (12) ou dans la paroi interne (1 1 ) du carter (3) de soufflante. 7. Turbojet engine according to one of claims 1 to 6, characterized in that the air suction means comprise air outlet orifices (15) formed downstream of the blower wheel (1) in the outer wall (12) or in the inner wall (1 1) of the fan casing (3).
8. Turboréacteur selon la revendication 7, caractérisé en ce que les orifices de sortie (15) des moyens d'aspiration d'air sont formés dans la paroi interne (1 1 ) du carter de soufflante (3) en aval d'un aubage redresseur (6) de sortie de la soufflante.  8. Turbojet engine according to claim 7, characterized in that the outlet orifices (15) of the air suction means are formed in the inner wall (1 1) of the fan casing (3) downstream of an airfoil. rectifier (6) output of the blower.
EP12702301.8A 2011-01-11 2012-01-05 Turbofan engine Active EP2663777B1 (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR1150224A FR2970302B1 (en) 2011-01-11 2011-01-11 DOUBLE FLOW TURBOREACTOR
PCT/FR2012/050027 WO2012095592A1 (en) 2011-01-11 2012-01-05 Turbofan engine

Publications (2)

Publication Number Publication Date
EP2663777A1 true EP2663777A1 (en) 2013-11-20
EP2663777B1 EP2663777B1 (en) 2014-11-05

Family

ID=44310870

Family Applications (1)

Application Number Title Priority Date Filing Date
EP12702301.8A Active EP2663777B1 (en) 2011-01-11 2012-01-05 Turbofan engine

Country Status (9)

Country Link
US (1) US9611865B2 (en)
EP (1) EP2663777B1 (en)
JP (1) JP2014502700A (en)
CN (1) CN103299084B (en)
BR (1) BR112013013690A2 (en)
CA (1) CA2819384A1 (en)
FR (1) FR2970302B1 (en)
RU (1) RU2589574C2 (en)
WO (1) WO2012095592A1 (en)

Families Citing this family (15)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2988146B1 (en) * 2012-03-15 2014-04-11 Snecma CARTER FOR WHEEL WITH IMPROVED TURBOMACHINE AUBES AND TURBOMACHINE EQUIPPED WITH SAID CARTER
FR3006722B1 (en) * 2013-06-06 2017-11-24 Snecma TURBOMACHINE COMPRESSOR DEDUSTING DEVICE
CN103423031A (en) * 2013-09-04 2013-12-04 西北工业大学 Pulse detonation engine tail nozzle
DE102013222514A1 (en) 2013-11-06 2015-05-07 MTU Aero Engines AG Sealing arrangement for a turbomachine
EP2871368B1 (en) 2013-11-12 2018-09-12 MTU Aero Engines GmbH Gas turbine compressor
FR3048727B1 (en) * 2016-03-14 2018-03-02 Safran Aircraft Engines AIR INLET DUCT FOR AN AIRCRAFT TURBOMACHINE
US11485486B2 (en) * 2016-05-18 2022-11-01 The University Of Toledo Active flow control for ducted fans and fan-in-wing configurations
US10683076B2 (en) 2017-10-31 2020-06-16 Coflow Jet, LLC Fluid systems that include a co-flow jet
CN108119406B (en) * 2018-01-11 2020-11-27 南京航空航天大学 Axial compressor circumferential large-interval small-through-hole casing
US11293293B2 (en) * 2018-01-22 2022-04-05 Coflow Jet, LLC Turbomachines that include a casing treatment
US11001389B2 (en) * 2018-11-29 2021-05-11 General Electric Company Propulsion engine thermal management system
CN111271322B (en) * 2018-12-05 2020-12-29 中国航发商用航空发动机有限责任公司 Adjustable stationary blade and compressor
FR3095241B1 (en) * 2019-04-17 2021-06-25 Safran Aircraft Engines Turbojet nacelle air inlet comprising a circulation pipe to promote a thrust reversal phase
GB2600584B (en) 2019-07-23 2024-03-06 Coflow Jet Llc Fluid systems and methods that address flow separation
CN114526263B (en) * 2022-02-17 2023-06-23 集美大学 Self-adaptive casing treatment device of axial-flow compressor and design method thereof

Family Cites Families (15)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB1291943A (en) * 1970-02-11 1972-10-04 Secr Defence Improvements in or relating to ducted fans
GB1342590A (en) * 1970-07-17 1974-01-03 Secr Defence Suppression of noise in gas turbine engines
US4086761A (en) * 1976-04-26 1978-05-02 The Boeing Company Stator bypass system for turbofan engine
SU926369A1 (en) * 1978-10-19 1982-05-07 Предприятие П/Я Р-6131 Fan casing
US4901520A (en) * 1988-08-12 1990-02-20 Avco Corporation Gas turbine pressurized cooling system
US6004095A (en) * 1996-06-10 1999-12-21 Massachusetts Institute Of Technology Reduction of turbomachinery noise
US6574965B1 (en) * 1998-12-23 2003-06-10 United Technologies Corporation Rotor tip bleed in gas turbine engines
CN1190597C (en) * 2000-03-20 2005-02-23 株式会社日立制作所 Turbine machine
US6585479B2 (en) * 2001-08-14 2003-07-01 United Technologies Corporation Casing treatment for compressors
RU2261999C2 (en) * 2003-01-23 2005-10-10 Открытое акционерное общество "Авиадвигатель" Aircraft turbofan engine
GB2407142B (en) * 2003-10-15 2006-03-01 Rolls Royce Plc An arrangement for bleeding the boundary layer from an aircraft engine
FR2882112B1 (en) * 2005-02-16 2007-05-11 Snecma Moteurs Sa HEAD SAMPLING OF HIGH PRESSURE COMPRESSOR MOBILE WHEELS FROM TURBOREACTOR
FR2892152B1 (en) * 2005-10-19 2007-11-23 Airbus France Sas TURBOMOTEUR WITH ATTENUATED JET NOISE
JP4893110B2 (en) * 2006-05-31 2012-03-07 株式会社Ｉｈｉ Axial fluid device
US7766280B2 (en) * 2007-05-29 2010-08-03 United Technologies Corporation Integral suction device with acoustic panel

Also Published As

Publication number Publication date
CN103299084B (en) 2015-09-09
JP2014502700A (en) 2014-02-03
US20130280046A1 (en) 2013-10-24
RU2589574C2 (en) 2016-07-10
RU2013137502A (en) 2015-02-20
FR2970302A1 (en) 2012-07-13
US9611865B2 (en) 2017-04-04
WO2012095592A1 (en) 2012-07-19
FR2970302B1 (en) 2015-07-17
BR112013013690A2 (en) 2016-09-06
CA2819384A1 (en) 2012-07-19
EP2663777B1 (en) 2014-11-05
CN103299084A (en) 2013-09-11

Similar Documents

Publication Publication Date Title
EP2663777B1 (en) Turbofan engine
EP3325345B1 (en) Aircraft comprising a propulsion assembly including a fan on the rear of the fuselage
FR3027053B1 (en) AIRCRAFT TURBOMACHINE STATOR
CA2975570C (en) Guide assembly with optimised aerodynamic performance
FR2995876A1 (en) INTEGRATED VARIABLE SECTION BLOWER ASSEMBLY WITH INTEGRATED PUSH INVERTER
EP2928769B1 (en) Propeller blade for turbo engine
FR2935349A1 (en) TURBOMACHINE WITH NON-CARINEATED PROPELLERS
CA2980688A1 (en) Discharge flow duct of a turbine engine comprising a vbv grating with variable setting
FR2982842A1 (en) PLANE
EP2569527B1 (en) Device for reducing the noise emitted by the jet of an aircraft propulsion engine
FR3067387B1 (en) AIR SUPPLY ECOPE FOR SUPPLYING A COOLING SYSTEM AND CONTROLLING THE GAMES OF A TURBINE
FR3090033A1 (en) DAWN DIRECTION AND BIFURCATION DIRECTOR SET FOR TURBOMACHINE
FR3068735B1 (en) TURBOREACTOR WITH LOW NOISE OF BLOW
EP3829975B1 (en) Turbomachine with coaxial propellers
US20230408091A1 (en) Cowl assembly for a gas turbine engine
BE1028097B1 (en) Turbomachine compressor blade, compressor and turbomachine fitted therewith
EP3959134B1 (en) Nacelle air intake with acoustic panel
FR2914705A1 (en) Compressor for airplane's jet engine, has air sampling hole emerging in inner-blade channel from fixed blades, exclusively in upstream region of channel which extends between specific percentages of blade length from edge of fixed blades
WO2023057704A1 (en) Outlet nozzle provided with chevrons for aeronautical thruster
FR3131600A1 (en) PROPULSION ASSEMBLY FOR AN AIRCRAFT
FR3121470A1 (en) Device for sealing and reinjecting a bypass flow for a turbine nozzle
WO2024100353A1 (en) Aero-propulsion system with improved propulsion efficiency
EP4073369A1 (en) Aero-propulsion system with improved propulsion efficiency
FR3104644A1 (en) Aeronautical propulsion system with improved propulsive efficiency
EP4229286A1 (en) Aeronautical propulsion system with improved propulsion efficiency

Legal Events

Date Code Title Description
PUAI Public reference made under article 153(3) epc to a published international application that has entered the european phase

Free format text: ORIGINAL CODE: 0009012

17P Request for examination filed

Effective date: 20130530

AK Designated contracting states

Kind code of ref document: A1

Designated state(s): AL AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HR HU IE IS IT LI LT LU LV MC MK MT NL NO PL PT RO RS SE SI SK SM TR

DAX Request for extension of the european patent (deleted)
GRAP Despatch of communication of intention to grant a patent

Free format text: ORIGINAL CODE: EPIDOSNIGR1

INTG Intention to grant announced

Effective date: 20140530

GRAS Grant fee paid

Free format text: ORIGINAL CODE: EPIDOSNIGR3

GRAA (expected) grant

Free format text: ORIGINAL CODE: 0009210

AK Designated contracting states

Kind code of ref document: B1

Designated state(s): AL AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HR HU IE IS IT LI LT LU LV MC MK MT NL NO PL PT RO RS SE SI SK SM TR

REG Reference to a national code

Ref country code: GB

Ref legal event code: FG4D

Free format text: NOT ENGLISH

REG Reference to a national code

Ref country code: CH

Ref legal event code: EP

REG Reference to a national code

Ref country code: AT

Ref legal event code: REF

Ref document number: 694804

Country of ref document: AT

Kind code of ref document: T

Effective date: 20141115

REG Reference to a national code

Ref country code: IE

Ref legal event code: FG4D

Free format text: LANGUAGE OF EP DOCUMENT: FRENCH

REG Reference to a national code

Ref country code: DE

Ref legal event code: R096

Ref document number: 602012003683

Country of ref document: DE

Effective date: 20141231

REG Reference to a national code

Ref country code: SE

Ref legal event code: TRGR

REG Reference to a national code

Ref country code: AT

Ref legal event code: MK05

Ref document number: 694804

Country of ref document: AT

Kind code of ref document: T

Effective date: 20141105

REG Reference to a national code

Ref country code: NL

Ref legal event code: VDEP

Effective date: 20141105

REG Reference to a national code

Ref country code: LT

Ref legal event code: MG4D

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: NL

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20141105

Ref country code: FI

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20141105

Ref country code: NO

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20150205

Ref country code: LT

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20141105

Ref country code: IS

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20150305

Ref country code: ES

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20141105

Ref country code: PT

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20150305

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: AT

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20141105

Ref country code: HR

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20141105

Ref country code: LV

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20141105

Ref country code: PL

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20141105

Ref country code: GR

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20150206

Ref country code: CY

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20141105

Ref country code: RS

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20141105

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: DK

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20141105

Ref country code: CZ

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20141105

Ref country code: SK

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20141105

Ref country code: EE

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20141105

REG Reference to a national code

Ref country code: DE

Ref legal event code: R097

Ref document number: 602012003683

Country of ref document: DE

REG Reference to a national code

Ref country code: CH

Ref legal event code: PL

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: LU

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20150105

PLBE No opposition filed within time limit

Free format text: ORIGINAL CODE: 0009261

STAA Information on the status of an ep patent application or granted ep patent

Free format text: STATUS: NO OPPOSITION FILED WITHIN TIME LIMIT

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: MC

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20141105

26N No opposition filed

Effective date: 20150806

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: CH

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20150131

Ref country code: LI

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20150131

REG Reference to a national code

Ref country code: IE

Ref legal event code: MM4A

REG Reference to a national code

Ref country code: FR

Ref legal event code: PLFP

Year of fee payment: 5

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: IE

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20150105

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: SI

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20141105

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: RO

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20141105

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: MT

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20141105

REG Reference to a national code

Ref country code: FR

Ref legal event code: PLFP

Year of fee payment: 6

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: BG

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20141105

Ref country code: SM

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20141105

Ref country code: HU

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT; INVALID AB INITIO

Effective date: 20120105

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: BE

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20150131

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: TR

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20141105

REG Reference to a national code

Ref country code: FR

Ref legal event code: PLFP

Year of fee payment: 7

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: MK

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20141105

REG Reference to a national code

Ref country code: FR

Ref legal event code: CD

Owner name: SAFRAN AIRCRAFT ENGINES, FR

Effective date: 20170719

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: AL

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20141105

PGFP Annual fee paid to national office [announced via postgrant information from national office to epo]

Ref country code: IT

Payment date: 20230103

Year of fee payment: 12

PGFP Annual fee paid to national office [announced via postgrant information from national office to epo]

Ref country code: GB

Payment date: 20231219

Year of fee payment: 13

PGFP Annual fee paid to national office [announced via postgrant information from national office to epo]

Ref country code: SE

Payment date: 20231219

Year of fee payment: 13

Ref country code: FR

Payment date: 20231219

Year of fee payment: 13

PGFP Annual fee paid to national office [announced via postgrant information from national office to epo]

Ref country code: DE

Payment date: 20231219

Year of fee payment: 13